Quench aperture body for a turbine engine combustor

ABSTRACT

An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.

This application is a divisional of U.S. patent application Ser. No.15/029,517 filed Apr. 14, 2016, which is a national stage application ofPCT Patent Application No. PCT/US14/063440 filed Oct. 31, 2014, whichclaims priority to U.S. Provisional Patent Application No. 61/899,570filed Nov. 4, 2013, all of which are hereby incorporated herein byreference in their entireties.

BACKGROUND OF THE INVENTION 1. Technical Field

This disclosure relates generally to a turbine engine and, moreparticularly, to a combustor for a turbine engine.

2. Background Information

A floating wall combustor for a turbine engine typically includes abulkhead that extends radially between inner and outer combustor walls.Each of the combustor walls includes a shell and a heat shield, whichdefines a radial side of a combustion chamber. Each of the combustorwalls also includes a plurality of quench apertures, which direct airfrom a plenum into the combustion chamber. Cooling cavities extendradially between the heat shield and the shell. These cooling cavitiesfluidly couple impingement apertures in the shell with effusionapertures in the heat shield.

There is a need in the art for an improved turbine engine combustor.

SUMMARY OF THE DISCLOSURE

According to an aspect of the invention, an assembly for a turbineengine is provided that includes a combustor wall. The combustor wallincludes a shell, a heat shield and an annular land. The heat shield isattached to the shell. The land extends vertically between the shell andthe heat shield. The land extends laterally between a land outer surfaceand an inner surface, which at least partially defines a quench aperturein the combustor wall. A lateral distance between the land outer surfaceand the inner surface varies around the quench aperture.

According to another aspect of the invention, another assembly for aturbine engine is provided that includes a combustor wall. The combustorwall includes a shell, a heat shield and an annular land. The heatshield is attached to the shell. The land extends between the shell andthe heat shield. The land at least partially defines a quench aperturein the combustor wall. The land is aligned with an aperture defined by asurface of the shell. The land has a land outer surface with across-sectional geometry with a different shape than a cross-sectionalgeometry of the surface of the shell.

According to another aspect of the invention, a heat shield is providedfor a turbine engine combustor wall through which a quench apertureradially extends. The heat shield includes a heat shield panel and anannular land. The heat shield panel includes a panel base and aplurality of rails. Each of the rails extends radially from the panelbase. The land is connected to the panel base and located between therails. The land extends laterally between a land outer surface and aninner surface that at least partially defines the quench aperture. Alateral distance between the land outer surface and the inner surfacechanges as the land extends around the inner surface.

The land outer surface may have a non-circular cross-sectional geometry.The land outer surface, for example, may have an oval cross-sectionalgeometry. In another example, the land outer surface may have apolygonal cross-sectional geometry. In another example, the land outersurface may include a plurality of facets. These facets may define aplurality of outside corners that are disposed around the land.Alternatively, the land outer surface may have a circularcross-sectional geometry.

The land may extend between the land outer surface and an inner surfacethat at least partially defines the quench aperture. The inner surfacemay have a circular cross-sectional geometry.

The land may extend between the land outer surface and an inner surfacethat at least partially defines the quench aperture. The inner surfacemay have a non-circular cross-sectional geometry.

The land may be aligned with an aperture defined by a surface of theshell that has a circular cross-sectional geometry.

The land may be aligned with an aperture defined by a surface of theshell that has a non-circular cross-sectional geometry.

A grommet may include the land and an annular rim, which extends fromthe land into or through an aperture defined by the shell. The rim mayhave a rim outer surface with a non-circular cross-sectional geometry.

A grommet may include the land and an annular rim, which extends fromthe land into or through an aperture defined by the shell. The rim mayhave a rim outer surface with a circular cross-sectional geometry.

A cavity may be defined between the shell and the heat shield. Thecavity may fluidly couple one or more cooling apertures defined by theshell with one or more cooling apertures defined by the heat shield.

A first of the cooling apertures defined by the heat shield may befurther defined by and extend through the land.

A combustor bulkhead may extend between the combustor wall and a secondcombustor wall. The combustor wall, the second combustor wall and thebulkhead may define a combustion chamber.

The cross-sectional geometry of the land outer surface may be anon-circular cross-sectional geometry. Alternatively, thecross-sectional geometry of the land outer surface may be a circularcross-sectional geometry.

A grommet may include the land and an annular rim, which extendsradially from the land and away from the panel base. The rim may extendbetween the inner surface and a rim outer surface with a circularcross-sectional geometry. The land outer surface may have a non-circularcross-sectional geometry. Alternatively, the land outer surface may havea circular cross-sectional geometry.

A grommet may include the land and an annular rim, which extendsradially from the land and away from the panel base. The rim may extendbetween the inner surface and a rim outer surface with a non-circularcross-sectional geometry. The land outer surface may have a non-circularcross-sectional geometry. Alternatively, the land outer surface may havea circular cross-sectional geometry.

The heat shield panel may include one or more mechanical attachmentsadapted to connect the heat shield panel to a combustor shell. Aplurality of effusion apertures may be defined by and extend through thepanel base.

The foregoing features and the operation of the invention will becomemore apparent in light of the following description and the accompanyingdrawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a side cutaway illustration of a geared turbine engine;

FIG. 2 is a side cutaway illustration of a portion of a combustorsection;

FIG. 3 is a perspective illustration of a portion of a combustor;

FIG. 4 is an illustration of a portion of a combustor wall with a ghostline of a shell land beneath a shell;

FIG. 5 is a cross-sectional illustration of the combustor wall portionof FIG. 4;

FIG. 6 is a side sectional illustration of a portion of the combustorwall;

FIG. 7 is a circumferential sectional illustration of combustor wallportion of FIG. 6;

FIG. 8 an illustration of a portion of a combustor wall with a ghostline of a shell land beneath a shell;

FIG. 9 is an illustration of a portion of a combustor wall with a ghostline of a shell land beneath a shell and a ghost line of the shell landof FIG. 8;

FIG. 10 is a cross-sectional illustration of a portion of an alternateembodiment combustor wall;

FIG. 11 is a cross-sectional illustration of a portion of an alternateembodiment combustor wall;

FIG. 12 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell;

FIG. 13 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell;

FIG. 14 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell;

FIG. 15 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell;

FIG. 16 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell;

FIG. 17 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell;

FIG. 18 is an illustration of a portion of an alternate embodimentcombustor wall with a ghost line of a shell land beneath a shell; and

FIG. 19 is an illustration of a portion of a combustor heat shield witha ghost line of a surface defining an aperture in a shell to which theheat shield is attached.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1 is a side cutaway illustration of a geared turbine engine 20.This turbine engine 20 extends along an axial centerline 22 between anupstream airflow inlet 24 and a downstream airflow exhaust 26. Theturbine engine 20 includes a fan section 28, a compressor section 29, acombustor section 30 and a turbine section 31. The compressor section 29includes a low pressure compressor (LPC) section 29A and a high pressurecompressor (HPC) section 29B. The turbine section 31 includes a highpressure turbine (HPT) section 31A and a low pressure turbine (LPT)section 31B. The engine sections 28-31 are arranged sequentially alongthe centerline 22 within an engine housing 34, which includes a firstengine case 36 (e.g., a fan nacelle) and a second engine case 38 (e.g.,a core nacelle).

Each of the engine sections 28, 29A, 29B, 31A and 31B includes arespective rotor 40-44. Each of the rotors 40-44 includes a plurality ofrotor blades arranged circumferentially around and connected to (e.g.,formed integral with or mechanically fastened, welded, brazed, adheredor otherwise attached to) one or more respective rotor disks. The fanrotor 40 is connected to a gear train 46 (e.g., an epicyclic gear train)through a shaft 47. The gear train 46 and the LPC rotor 41 are connectedto and driven by the LPT rotor 44 through a low speed shaft 48. The HPCrotor 42 is connected to and driven by the HPT rotor 43 through a highspeed shaft 50. The shafts 47, 48 and 50 are rotatably supported by aplurality of bearings 52. Each of the bearings 52 is connected to thesecond engine case 38 by at least one stator element such as, forexample, an annular support strut.

Air enters the turbine engine 20 through the airflow inlet 24, and isdirected through the fan section 28 and into an annular core gas path 54and an annular bypass gas path 56. The air within the core gas path 54may be referred to as “core air”. The air within the bypass gas path 56may be referred to as “bypass air”.

The core air is directed through the engine sections 29-31 and exits theturbine engine 20 through the airflow exhaust 26. Within the combustorsection 30, fuel is injected into an annular combustion chamber 58 andmixed with the core air. This fuel-core air mixture is ignited to powerthe turbine engine 20 and provide forward engine thrust. The bypass airis directed through the bypass gas path 56 and out of the turbine engine20 through a bypass nozzle 60 to provide additional forward enginethrust. Alternatively, the bypass air may be directed out of the turbineengine 20 through a thrust reverser to provide reverse engine thrust.

FIG. 2 illustrates an assembly 62 of the turbine engine 20. The turbineengine assembly 62 includes a combustor 64 arranged within a plenum 66(e.g., an annular plenum) of the combustor section 30. This plenum 66receives compressed core air from the HPC section 29B, and provides thereceived core air to the combustor 64 as described below in furtherdetail.

The turbine engine assembly 62 also includes one or more fuel injectorassemblies 68. Each fuel injector assembly 68 may include a fuelinjector 70 mated with a swirler 72. The fuel injector 70 injects thefuel into the combustion chamber 58. The swirler 72 directs some of thecore air from the plenum 66 into the combustion chamber 58 in a mannerthat facilitates mixing the core air with the injected fuel. Quenchapertures 74 in walls of the combustor 64 direct additional core airinto the combustion chamber 58 for combustion; e.g., tostoichiometrically lean the fuel-core air mixture.

The combustor 64 may be configured as an annular floating wallcombustor. The combustor 64 of FIGS. 2 and 3, for example, includes acombustor bulkhead 76, a tubular combustor inner wall 78, and a tubularcombustor outer wall 80. The bulkhead 76 extends radially between and isconnected to the inner wall 78 and the outer wall 80. The inner wall 78and the outer wall 80 each extends axially along the centerline 22 fromthe bulkhead 76 towards the turbine section 31A, thereby defining thecombustion chamber 58.

Referring to FIG. 2, the inner wall 78 and the outer wall 80 may eachhave a multi-walled structure; e.g., a hollow dual-walled structure. Theinner wall 78 and the outer wall 80 of FIG. 2, for example, eachincludes a tubular combustor shell 82, a tubular combustor heat shield84, and one or more cooling cavities 86 (e.g., impingement cavities)between the shell 82 and the heat shield 84. The inner wall 78 and theouter wall 80 also each includes one or more quench aperture bodies 88(e.g., grommets), which are arranged circumferentially around thecenterline 22. Each quench aperture body 88 partially or fully defines arespective one of the quench apertures 74 as described below in furtherdetail.

The shell 82 extends circumferentially around the centerline 22. Theshell 82 extends axially along the centerline 22 between an upstream end90 and a downstream end 92. The shell 82 is connected to the bulkhead 76at the upstream end 90. The shell 82 may be connected to a stator vaneassembly 94 or the HPT section 31A at the downstream end 92.

Referring to FIG. 3, the shell 82 includes a plurality of apertures 96arranged circumferentially around the centerline 22. Referring to FIGS.4 and 5, each of the apertures 96 may be defined by a surface 98 of theshell 82 that extends radially between opposing side surfaces 100 and102 of the shell 82. The surface 98 of FIG. 4 has a circularcross-sectional geometry.

Referring to FIG. 2, the heat shield 84 extends circumferentially aroundthe centerline 22. The heat shield 84 extends axially along thecenterline 22 between an upstream end and a downstream end. The heatshield 84 may include one or more heat shield panels 104. These panels104 may be arranged into one or more axial sets. The axial sets arearranged at discrete locations along the centerline 22. The panels 104in each set are disposed circumferentially around the centerline 22 andform a hoop. Alternatively, the heat shield 84 may be configured fromone or more tubular bodies.

FIGS. 6 and 7 illustrate exemplary portions of one of the walls 78, 80.It should be noted that the shell 82 and the heat shield 84 eachrespectively include one or more cooling apertures 106 and 108 (see FIG.5) as described below in further detail. For ease of illustration,however, the shell 82 and the heat shield 84 of FIGS. 6 and 7 are shownwithout the cooling apertures 106 and 108.

Each of the panels 104 includes a panel base 110 and one or more panelrails (e.g., rails 112-116). The panel base 110 may be configured as agenerally curved (e.g., arcuate) plate. The panel base 110 extendsaxially between an upstream axial end 118 and a downstream axial end120. The panel base 110 extends circumferentially between opposingcircumferential ends 122 and 124.

The panel rails may include one or more circumferentially extending endrails 112 and 113 and one more axially extending end rails 114 and 115.The panel rails may also include at least one intermediate rail 116.Each of the panel rails 112-116 of the outer wall 80 extends radiallyout from the panel base 110 (see FIG. 2). Each of the panel rails112-116 of the inner wall 78 extends radially in from the panel base 110(FIG. 2). The rail 112 is arranged at (e.g., on, adjacent or proximate)the axial end 118. The rail 113 is arranged at the axial end 120. Therails 114 and 115 extend axially between and are connected to the rails112 and 113. The rail 114 is arranged at the circumferential end 122.The rail 115 is arranged at the circumferential end 124. The rail 116 isarranged axially between the rails 112 and 113, and extends and isconnected circumferentially between the rails 114 and 115.

Each quench aperture body 88 extends within a respective one of thecooling cavities 86. Each quench aperture body 88, for example, may bearranged circumferentially between the rails 114 and 115 of a respectiveone of the panels 104. Each quench aperture body 88 may be arrangedaxially between the rails 112 and 116 of a respective one of the panels104.

One or more of the quench aperture bodies 88 are connected to arespective one of the panels 104. The quench aperture body 88 of FIG. 5,for example, is formed integral with the respective panel base 110. Thequench aperture body 88 and the panel base 110, for example, may be castand/or machined as a unitary body. The quench aperture body 88, however,may alternatively be formed as a discrete element and subsequentlyattached (e.g., bonded and/or mechanically fastened) to the respectivepanel base 110.

Referring to FIGS. 4 and 5, each quench aperture body 88 includes anannular shell land 126 and an annular rim 128. The land 126 extendsradially from the respective panel base 110 to a distal land surface130. The land 126 extends laterally between a land outer surface 132 anda body inner surface 134, which defines the respective quench aperture74.

The outer surface 132 of FIG. 4 has an oval cross-sectional geometrywith a major axis and a minor axis. The major axis extendscircumferentially around the centerline 22. The minor axis extends alongthe centerline 22. The cross-sectional geometry of the outer surface132, however, is not limited to the foregoing orientation. The innersurface 134 of FIG. 4 has a circular cross-sectional geometry.Therefore, with the land 126 configuration of FIGS. 4 and 5, a lateraldistance D between the land out surface 132 and the inner surface 134may change as the land 126 extends around the inner surface 134 and therespective quench aperture 74. The lateral distance D₁ along the majoraxis of the land outer surface 132, for example, is greater than thelateral distance D₂ along the minor axis of the land outer surface 132.

The rim 128 is connected to the land 126. The rim 128 extends radiallyfrom the land 126 and the land surface 130 to a distal rim surface 136.The rim 128 extends laterally between a rim outer surface 138 and theinner surface 134. The outer surface 138 of FIG. 4 has a circularcross-sectional geometry.

Referring to FIG. 2, the heat shield 84 of the inner wall 78circumscribes the shell 82 of the inner wall 78, and defines a radialinner side of the combustion chamber 58. The heat shield 84 of the outerwall 80 is arranged radially within the shell 82 of the outer wall 80,and defines a radial outer side of the combustion chamber 58 that isopposite the inner side. Referring now to FIG. 5, each quench aperturebody 88 is (e.g., axially and circumferentially) aligned and mated witha respective one of the apertures 96. Each rim 128, for example, extendsradially through (or into) a respective one of the apertures 96. Eachland surface 130 may engage (e.g., slidingly contact) the surface 100and, thus, the shell 82.

Referring to FIG. 2, each heat shield 84 and, more particularly, eachpanel 104 may be respectively attached to the shell 82 by a plurality ofmechanical attachments 140 (see also FIG. 6). The shells 82 and the heatshields 84 thereby respectively form the cooling cavities 86 in theinner and the outer walls 78 and 80. For example, referring to FIGS. 6and 7, each cooling cavity 86 may extend circumferentially between therails 114 and 115 of a respective one of the panels 104. Some of thecooling cavities 86 may extend axially between the rails 112 and 116 ofa respective one of the panels 104. Some of the cooling cavities 86 mayextend axially between the rails 113 and 116 of a respective one of thepanels 104. Each cooling cavity 86 extends radially between the shell 82and the panel base 110 of a respective one of the panels 104.

Referring to FIG. 5, each cooling cavity 86 may fluidly couple one ormore of the cooling apertures 106 in the shell 82 with one or more ofthe cooling apertures 108 in the heat shield 84. One or more of thecooling apertures 106 may each be configured as an impingement aperture,which extends radially through the shell 82. One or more of the coolingapertures 108 may each be configured as an effusion aperture, whichextends radially through the heat shield 84 and, more particularly, therespective panel base 110.

During turbine engine operation, core air from the plenum 66 is directedinto each cooling cavity 86 through respective cooling apertures 106.This core air (hereinafter referred to as “cooling air”) may impingeagainst the panel base 110, thereby impingement cooling the heat shield84. The cooling air within each cooling cavity 86 is subsequentlydirected through respective cooling apertures 108 and into thecombustion chamber 58, thereby film cooling a downstream portion of theheat shield 84. Within each cooling aperture 108, the cooling air mayalso cool the heat shield 84 through convective heat transfer.

As a temperature of the heat shield 84 increases, thermal distortion ofthe heat shield 84 may cause one or more of the quench aperture bodies88 to move circumferentially and/or axially relative to the shell 82.Referring to FIG. 8, a land 802 of a typical quench aperture grommet 804has a circular geometry that is oversized to accommodate the foregoingthermally induce movement between the heat shield and the shell 806.This oversize geometry land 802, however, may block cooling air fromimpinging against the panel base of the heat shield near the quenchaperture 808. A region of the panel base below and proximate the land802 therefore may be subjected to relatively high temperatures and,thus, thermally induced stresses.

The inventors of the present invention have recognized that a magnitudeof the circumferential movement may be greater than a magnitude of theaxial movement, or vice versa depending upon the configuration of thecombustor 64. Thus, referring to FIG. 9, the elongated geometry of eachland 126 may be tailored to accommodate skewed thermally inducedmovement between the heat shield 84 and the shell 82; e.g., the distanceD₁ may be sized greater than the distance D₂ to accommodate the greatermagnitude of circumferential thermal expansion. In addition, theelongated geometry of each land 126 may enable more of the cooling airdirected from the cooling apertures 106 to impinge and/or flowrelatively close to the quench aperture 74 in regions 142 aligned withthe minor axis. Similarly, the elongated geometry of each land 126 mayalso or alternatively enable some of the cooling apertures 108 (notshown) to be located relatively close to the quench aperture 74 in theregions 142. Notably, these regions 142 include portions of the panelbase 110 which would otherwise be blocked by the typical circular landas illustrated by the dashed line 144. The cooling quench aperturebodies 88 therefore may increase the cooling effectiveness of the heatshield 84 as compared to the circular land 802 embodiment of FIG. 8.

In some embodiments, referring to FIG. 10, one or more of the coolingapertures 108 may be defined by and/or extend (e.g., radially) through arespective one of the lands 126 and/or through the panel base 110. Inthis manner, additional thermal energy may be convectively transferredinto the cooling air thereby further reducing the temperature of theland 126 and the adjacent portion of the panel base 110.

In some embodiments, referring to FIG. 11, one or more of the quenchaperture bodies 88 may each be configured without the rim 128 (see FIG.10). In this manner, the surface 98 of the shell 82 may from a firstportion 146 of a respective one of the quench apertures 74. The innersurface 134 of the quench aperture body 88 may form a second portion 148of a respective one of the quench apertures 74, which is adjacent thefirst portion 146.

One or more of the surfaces 98, 132, 134 and 138 may each have variousconfigurations other than those described above. For example, one ormore of the surfaces 98, 132, 134 and 138 may each have a circularcross-sectional geometry. One or more of the surfaces 98, 132, 134 and138 may also or alternatively each have a non-circular cross-sectionalgeometry and/or a compound cross-sectional geometry. Examples of anon-circular cross-sectional geometry include, but are not limited to,an oval cross-sectional geometry and a polygonal cross-sectionalgeometry. Examples of a polygonal cross-sectional geometry include, butare not limited to, a rectangular cross-sectional geometry, a triangularcross-sectional geometry, a hexagonal cross-sectional geometry, anoctagonal cross-sectional geometry, a star-shaped cross-sectionalgeometry, and an asterisk-shaped cross-sectional geometry. Examples of acompound cross-sectional geometry include, but are not limited to, across-sectional geometry having a (e.g., generally circular or oval)central portion surrounded by a plurality of peripheral portions withsmaller similar (e.g., circular or oval) shapes or different (e.g.,triangular, polygonal) shapes; e.g., one or more pedals around a centralportion. Some examples of these different surface configurations aredescribed below and illustrated in FIGS. 12-16, some of which do notshow the apertures 106 for ease of illustration. The present invention,however, is not limited to any particular surface configurations.

In some embodiments, referring to FIG. 12, the surface 98 may have anoval cross-sectional geometry. The outer surface 132 may have an ovalcross-sectional geometry. The inner surface 134 may have a circularcross-sectional geometry. The outer surface 138 may have an ovalcross-sectional geometry. The cross-sectional geometries of one or moreof the surfaces 132, 134 and 138 may be disproportional to thecross-sectional geometry of the surface 98; e.g., ratios of lengthsalong the minor and major axes may be different.

In some embodiments, referring to FIG. 13, the surface 98 may have anoval cross-sectional geometry. The outer surface 132 may have an ovalcross-sectional geometry. The inner surface 134 may have an ovalcross-sectional geometry. The outer surface 138 may have an ovalcross-sectional geometry. The cross-sectional geometries of one or moreof the surfaces 134 and 138 may be disproportional to thecross-sectional geometry of the surface 98. The cross-sectional geometryof one of the surfaces 98, 134 and 138, however, may be proportional tothe cross-sectional geometry of the surface 132; e.g., ratios of lengthsalong the minor and major axes may be substantially equal.

In some embodiments, referring to FIG. 14, the surface 98 may have anoval cross-sectional geometry. The outer surface 132 may have an ovalcross-sectional geometry. The inner surface 134 may have an ovalcross-sectional geometry. The outer surface 138 may have an ovalcross-sectional geometry. The cross-sectional geometries of one or moreof the surfaces 132, 134 and 138 may be disproportional to thecross-sectional geometry of the surface 98.

In some embodiments, referring to FIG. 15, the surface 98 may have anoval cross-sectional geometry. The outer surface 132 may have an ovalcross-sectional geometry. The inner surface 134 may have an ovalcross-sectional geometry. The outer surface 138 may have an ovalcross-sectional geometry. The cross-sectional geometries of one or moreof the surfaces 132, 134 and 138 may be proportional to thecross-sectional geometry of the surface 98.

In some embodiments, referring to FIG. 16, the inner surface 134 mayhave a circular cross-sectional geometry. The outer surface 138 may havea circular cross-sectional geometry. The surface 98 may have a generallyrectangular (or race-track) cross-sectional geometry with, for example,eased corners. In this manner, the surface 98 defines the aperture 96with an elongated geometry that permits increased thermally inducedmajor axis (e.g., circumferential) movement between the rim 128 and theshell 82. The land outer surface 132 may also have a generallyrectangular (or race-track) cross-sectional geometry that enables a sealto be maintained between the land 126 and the shell 82 during theafore-described major axis movement.

In some embodiments, referring to FIG. 17, the major and minor axes ofthe inner surface 134 and the quench aperture 74 may be opposite orotherwise different than the major and minor axes of one or more of thesurfaces 98 and 132 and/or the aperture 96.

In some embodiments, referring to FIGS. 18 and 19, the surface 132 mayinclude a plurality of facets 150. These facets 150 are arrangedcircumferentially around the land 126. Some of the facets 150 arerespectively joined at a plurality of outside corners 152. Some of thefacets 150 are respectively joined at a plurality of inside corners 154.The outside and the inside corners 152 and 154 are arrangedcircumferentially around the land 126. One or more of the corners 152,154 may each be a relatively sharp corner as illustrated in FIG. 18. Oneor more of the corners 152, 154 may each be a relatively dull (e.g.,rounded or eased) corner as illustrated in FIG. 19.

The facets 150 respectively form a plurality of indentations 156 thatextend into the land 126 to the inside corners 154. The cooling airwithin the cavity 86 therefore may flow into the indentations 156 andprovide additional impingement and/or convective cooling to the panelbase 110 and the quench aperture body 88. Referring to FIG. 16, theindentations 156 also enable one or more of the cooling apertures 108 tobe located relatively close to the surface 134 and the quench aperture74 to further increase panel base 110 and/or quench aperture body 88cooling.

The terms “upstream”, “downstream”, “inner” and “outer” are used toorientate the components of the turbine engine assembly 62 and thecombustor 64 described above relative to the turbine engine 20 and itscenterline 22. A person of skill in the art will recognize, however, oneor more of these components may be utilized in other orientations thanthose described above. The present invention therefore is not limited toany particular spatial orientations.

The turbine engine assembly 62 may be included in various turbineengines other than the one described above. The turbine engine assembly62, for example, may be included in a geared turbine engine where a geartrain connects one or more shafts to one or more rotors in a fansection, a compressor section and/or any other engine section.Alternatively, the turbine engine assembly 62 may be included in aturbine engine configured without a gear train. The turbine engineassembly 62 may be included in a geared or non-geared turbine engineconfigured with a single spool, with two spools (e.g., see FIG. 1), orwith more than two spools. The turbine engine may be configured as aturbofan engine, a turbojet engine, a propfan engine, or any other typeof turbine engine. The present invention therefore is not limited to anyparticular types or configurations of turbine engines.

While various embodiments of the present invention have been disclosed,it will be apparent to those of ordinary skill in the art that many moreembodiments and implementations are possible within the scope of theinvention. For example, the present invention as described hereinincludes several aspects and embodiments that include particularfeatures. Although these features may be described individually, it iswithin the scope of the present invention that some or all of thesefeatures may be combined within any one of the aspects and remain withinthe scope of the invention. Accordingly, the present invention is not tobe restricted except in light of the attached claims and theirequivalents.

What is claimed is:
 1. An assembly for a turbine engine, the assemblycomprising: a combustor wall including a shell, a heat shield and anannular quench aperture body; the heat shield attached to the shell; andthe annular quench aperture body extending vertically between the shelland the heat shield and laterally between a body outer surface and aninner surface, the inner surface at least partially defining a quenchaperture in the combustor wall, the annular quench aperture body beingrigidly connected to the heat shield wherein a lateral distance betweenthe body outer surface and the inner surface varies around the quenchaperture, and the lateral distance is measured in a reference plane thatis vertically between the shell and the heat shield; and wherein theannular quench aperture body is configured to move relative to theshell.
 2. The assembly of claim 1, wherein the body outer surface has apolygonal cross-sectional geometry.
 3. The assembly of claim 2, whereinthe body outer surface includes a plurality of facets; and the pluralityof facets define outside corners that are disposed around the annularquench aperture body.
 4. The assembly of claim 1, wherein the innersurface has a non-circular cross-sectional geometry.
 5. The assembly ofclaim 1, wherein the annular quench aperture body is aligned with anaperture defined by a surface of the shell, and the surface of the shellhas a circular cross-sectional geometry.
 6. The assembly of claim 1,wherein the annular quench aperture body includes an annular land and anannular rim; and the annular rim extends from the annular land into orthrough an aperture defined by the shell, and the annular rim has a rimouter surface with a non-circular cross-sectional geometry.
 7. Anassembly for a turbine engine, the assembly comprising: a combustor wallincluding a shell, a heat shield and an annular quench aperture body;the heat shield attached to the shell; and the annular quench aperturebody extending vertically between the shell and the heat shield andlaterally between a body outer surface and an inner surface, the innersurface at least partially defining a quench aperture in the combustorwall; wherein a lateral distance between the body outer surface and theinner surface varies around the quench aperture; wherein the body outersurface has a polygonal cross-sectional geometry and the inner surfacehas a circular cross-sectional geometry when viewed in a commonreference plane; and wherein the annular quench aperture body slidinglycontacts the shell.
 8. The assembly of claim 7, wherein the annularquench aperture body includes an annular land and an annular rim; theannular land projects vertically out from the heat shield to a distalsurface abutted vertically against and slidably contacting the shell;and the annular rim projects vertically out from the annular land intoor through an aperture defined by the shell.
 9. The assembly of claim 8,wherein the annular land is fixedly connected to the heat shield.